CA2627492A1 - Modular avionics system of an aircraft - Google Patents
Modular avionics system of an aircraft Download PDFInfo
- Publication number
- CA2627492A1 CA2627492A1 CA002627492A CA2627492A CA2627492A1 CA 2627492 A1 CA2627492 A1 CA 2627492A1 CA 002627492 A CA002627492 A CA 002627492A CA 2627492 A CA2627492 A CA 2627492A CA 2627492 A1 CA2627492 A1 CA 2627492A1
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- CA
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- Prior art keywords
- aircraft
- core processor
- cabinets
- module
- modules
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
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- 101100001773 Oryza sativa subsp. japonica AOC gene Proteins 0.000 claims abstract description 7
- 238000012545 processing Methods 0.000 claims abstract description 5
- 238000012432 intermediate storage Methods 0.000 claims abstract description 4
- 101000957815 Culex pipiens Alpha-glucosidase Proteins 0.000 claims description 4
- 230000006870 function Effects 0.000 description 6
- 230000008901 benefit Effects 0.000 description 3
- 230000005540 biological transmission Effects 0.000 description 2
- 238000013461 design Methods 0.000 description 2
- 230000002457 bidirectional effect Effects 0.000 description 1
- 230000008859 change Effects 0.000 description 1
- 238000004891 communication Methods 0.000 description 1
- 230000003455 independent Effects 0.000 description 1
- 230000010354 integration Effects 0.000 description 1
- 238000000034 method Methods 0.000 description 1
- 230000004048 modification Effects 0.000 description 1
- 238000012986 modification Methods 0.000 description 1
- 238000002345 optical interference microscopy Methods 0.000 description 1
- 230000008569 process Effects 0.000 description 1
- 230000009467 reduction Effects 0.000 description 1
Classifications
-
- G—PHYSICS
- G05—CONTROLLING; REGULATING
- G05B—CONTROL OR REGULATING SYSTEMS IN GENERAL; FUNCTIONAL ELEMENTS OF SUCH SYSTEMS; MONITORING OR TESTING ARRANGEMENTS FOR SUCH SYSTEMS OR ELEMENTS
- G05B19/00—Programme-control systems
- G05B19/02—Programme-control systems electric
- G05B19/04—Programme control other than numerical control, i.e. in sequence controllers or logic controllers
- G05B19/042—Programme control other than numerical control, i.e. in sequence controllers or logic controllers using digital processors
- G05B19/0421—Multiprocessor system
-
- G—PHYSICS
- G05—CONTROLLING; REGULATING
- G05B—CONTROL OR REGULATING SYSTEMS IN GENERAL; FUNCTIONAL ELEMENTS OF SUCH SYSTEMS; MONITORING OR TESTING ARRANGEMENTS FOR SUCH SYSTEMS OR ELEMENTS
- G05B2219/00—Program-control systems
- G05B2219/20—Pc systems
- G05B2219/25—Pc structure of the system
- G05B2219/25033—Pc structure of the system structure, control, syncronization, data, alarm, connect I-O line to interface
-
- G—PHYSICS
- G05—CONTROLLING; REGULATING
- G05B—CONTROL OR REGULATING SYSTEMS IN GENERAL; FUNCTIONAL ELEMENTS OF SUCH SYSTEMS; MONITORING OR TESTING ARRANGEMENTS FOR SUCH SYSTEMS OR ELEMENTS
- G05B2219/00—Program-control systems
- G05B2219/20—Pc systems
- G05B2219/25—Pc structure of the system
- G05B2219/25314—Modular structure, modules
Abstract
In a modular avionics system comprising several cabinets that are arranged at various locations in an aircraft and that are interconnected in a network, which cabinets are used for controlling or processing signals from and to sensors, actuators and other systems of the aircraft, it is proposed that the system comprise parallel processors, for example transputers; the cabinets comprise at least two core processor modules (CPMl, CPM2) and at least two input/output modules (IOM1, IOM2); the in- put/output modules (IOM1, IOM2) serve as interfaces to the systems to be con¬ trolled, and serve for the control and intermediate storage of the data flowing into and out of the cabinet; each core processor module (CPMl , CPM2) communicates independently with each IOM module and CPM module by way of links; and in each core processor a number of independent system programs works under the control of an operating system. By being able to do without the backplane bus that is required in conventional systems the efficiency is enhanced and changing applications is facilitated.
Description
MODULAR AVIONICS SYSTEM OF AN AIRCRAFT
Reference to related applications:
This application claims the benefit of the filing date of German Patent Application No. 10 2005 055 000.2 filed November 18, 2005, the disclosure of which applications is hereby incorporated herein by reference.
Field of the invention:
The invention relates to a modular avionics system of an aircraft according to the char-acterising portion of claim 1.
Technical background of the invention:
The avionics architecture presently used in aircraft is based on the specifications accord-ing to Arinc 700. According to these specifications, manufacturers of avionics devices provide a specially tailored controller that is accommodated in a line replaceable unit (LRU) for each function. Each LRU thus comprises the following components:
power supply, processor, I/O modules and others.
With the use of integrated modular avionics, improved integration by utilising the com-puting power of microprocessors for several tasks (resource sharing) becomes possible.
A reduction in the number of components, and standardisation of components are fur-ther advantages.
A known IMA- (integrated modular avionics) architecture provides several cabinets at various locations in the aircraft. For data exchange all models are interconnected by way of a backplane bus (Arinc 659, currently SAFEbus by Honeywell).
Sensor data of the various functions are fed to the core processor by way of the input modules and the backplane bus. In the core processor, an operating system determines which system software (application) is to be used at what time. The data is directly transmitted to the associated software. After completion of processing, the data is re-turned via the backplane bus to the output module from where it is transmitted to actua-tors or other systems.
The cabinets in turn are interconnected in a network (Arinc 629).
In this solution the backplane bus represents a bottleneck. In order to prevent a collapse, the data has to be determined deterministically for transmission.
Several attempted solutions for managing these problems are known. For example, in US 5,506,963 a real-time processor system is implemented in that a coprocessor is used which manages the time slices of a specified timeframe for the processor.
These time slices can be of different duration, with allocation to one or several installed layouts being determined by the function/application. In this solution a central databus is used with deterministic data traffic. Tools for setting up the data traffic are necessary, data conflicts can arise, and changes in the function are only possible if at the same time the bus data structure is adapted.
According to US 4,658,359 a computer is used to manage a plurality of computers in a complex avionics system. A single user can thus process a plurality of func-tions/applications from one display screen. Here, operation and modification of applica-tions of a communication system by means of an executive computer are in the fore-ground. The use as an integrated modular avionics system with transputers is not con-sidered.
According to US 5,361,367 a number of single-instruction multiple data (SIMD) proc-essors are accommodated in a computer. Two sets of respectively three individual proc-essors are controlled by a master computer and are connected to a plurality of registers.
These SIMD processors are linked, for data exchange, to form a ring arrangement or pipeline arrangement. This is a high-speed processor. However, the data bus problems at high data rates and in the case of distributed tasks remain.
Reference to related applications:
This application claims the benefit of the filing date of German Patent Application No. 10 2005 055 000.2 filed November 18, 2005, the disclosure of which applications is hereby incorporated herein by reference.
Field of the invention:
The invention relates to a modular avionics system of an aircraft according to the char-acterising portion of claim 1.
Technical background of the invention:
The avionics architecture presently used in aircraft is based on the specifications accord-ing to Arinc 700. According to these specifications, manufacturers of avionics devices provide a specially tailored controller that is accommodated in a line replaceable unit (LRU) for each function. Each LRU thus comprises the following components:
power supply, processor, I/O modules and others.
With the use of integrated modular avionics, improved integration by utilising the com-puting power of microprocessors for several tasks (resource sharing) becomes possible.
A reduction in the number of components, and standardisation of components are fur-ther advantages.
A known IMA- (integrated modular avionics) architecture provides several cabinets at various locations in the aircraft. For data exchange all models are interconnected by way of a backplane bus (Arinc 659, currently SAFEbus by Honeywell).
Sensor data of the various functions are fed to the core processor by way of the input modules and the backplane bus. In the core processor, an operating system determines which system software (application) is to be used at what time. The data is directly transmitted to the associated software. After completion of processing, the data is re-turned via the backplane bus to the output module from where it is transmitted to actua-tors or other systems.
The cabinets in turn are interconnected in a network (Arinc 629).
In this solution the backplane bus represents a bottleneck. In order to prevent a collapse, the data has to be determined deterministically for transmission.
Several attempted solutions for managing these problems are known. For example, in US 5,506,963 a real-time processor system is implemented in that a coprocessor is used which manages the time slices of a specified timeframe for the processor.
These time slices can be of different duration, with allocation to one or several installed layouts being determined by the function/application. In this solution a central databus is used with deterministic data traffic. Tools for setting up the data traffic are necessary, data conflicts can arise, and changes in the function are only possible if at the same time the bus data structure is adapted.
According to US 4,658,359 a computer is used to manage a plurality of computers in a complex avionics system. A single user can thus process a plurality of func-tions/applications from one display screen. Here, operation and modification of applica-tions of a communication system by means of an executive computer are in the fore-ground. The use as an integrated modular avionics system with transputers is not con-sidered.
According to US 5,361,367 a number of single-instruction multiple data (SIMD) proc-essors are accommodated in a computer. Two sets of respectively three individual proc-essors are controlled by a master computer and are connected to a plurality of registers.
These SIMD processors are linked, for data exchange, to form a ring arrangement or pipeline arrangement. This is a high-speed processor. However, the data bus problems at high data rates and in the case of distributed tasks remain.
According to EP 0,570,729 A2 an individual chip houses eight processors that are linked by way of a cube topology. Compared to conventional microprocessors there are fewer pins, and the memory time is shortened. Here again, the solution shows an im-proved high-speed processor chip.
Summary of the invention:
Consequently it is the object of the invention to design a modular avionics system such that with implementation of deterministic data traffic, no central data bus is used, wherein no data conflicts must occur in the data buses considered.
This object is met by the measures according to claim 1. An expedient embodiment is provided with claim 2.
According to the invention it is proposed that the system comprises parallel processors, for example transputers; the cabinets comprise at least two core processor modules (CPM 1, CPM2) and at least two input/output modules (IOM1, IOM2); the input output modules (IOMl, IOM2) serve as interfaces to the system to be controlled and serve for control and intermediate storage of the data flowing into and out of the cabinet; each core processor module (CPM1, CPM2) communicate independently with each IOM
module and CPM module by way of links; and in each core processor a number of inde-pendent system programs work under the control of an operating system.
With the use of parallel processors, for example transputers, the bottleneck represented by the backplane bus no longer exists, because these parallel processors can communi-cate with several processors by way of separate direct data lines (links).
Short description of the drawinjzs:
Further details of the invention are shown in the drawings, which show prior art and the invention respectively, as follows:
Summary of the invention:
Consequently it is the object of the invention to design a modular avionics system such that with implementation of deterministic data traffic, no central data bus is used, wherein no data conflicts must occur in the data buses considered.
This object is met by the measures according to claim 1. An expedient embodiment is provided with claim 2.
According to the invention it is proposed that the system comprises parallel processors, for example transputers; the cabinets comprise at least two core processor modules (CPM 1, CPM2) and at least two input/output modules (IOM1, IOM2); the input output modules (IOMl, IOM2) serve as interfaces to the system to be controlled and serve for control and intermediate storage of the data flowing into and out of the cabinet; each core processor module (CPM1, CPM2) communicate independently with each IOM
module and CPM module by way of links; and in each core processor a number of inde-pendent system programs work under the control of an operating system.
With the use of parallel processors, for example transputers, the bottleneck represented by the backplane bus no longer exists, because these parallel processors can communi-cate with several processors by way of separate direct data lines (links).
Short description of the drawinjzs:
Further details of the invention are shown in the drawings, which show prior art and the invention respectively, as follows:
Fig. 1 shows the diagrammatic configuration of an IMA cabinet according to prior art; and Fig. 2 shows the configuration according to the invention.
Detailed description of exemplary embodiments:
A known IMA- (integrated modular avionics) architecture according to Fig. 1 provides several cabinets at various locations in the aircraft. Each cabinet comprises the follow-ing modules: power supply modules (PSM), I/O modules (IOM), and core processing modules (CPM). All modules receive electrical power from the power supply and are interconnected for data exchange by way of a backplane bus (Arinc 659 - a SAFEbus by Honeywell).
The sensor data of the various functions are transmitted to the core processor by way of the input modules and the backplane bus. In the core processor an operating system de-termines which system software (application) is to be used at what time. The data is directly transmitted to the associated software. After completion of processing, the data are returned via the backplane bus to the output module from where they are transmitted to actuators or other systems. The cabinets in turn are interconnected in a network (Arinc 629).
In this solution the backplane bus represents a bottleneck. In order to prevent a collapse, the data haveto be determined deterministically for transmission.
In order to obviate the need for such a backplane bus and in this way to avoid the asso-ciated bottleneck, an architecture for a cabinet is proposed, which architecture is based on parallel processors, for example transputers. The IMA architecture according to Fig.
2 shows this configuration.
For reasons of redundancy the cabinet comprises at least two core processor modules (CPM1, CPM2) and at least two input/output modules (IOM1, IOM2).
The IOMs are used as an interface to the sensors, actuators, systems and buses. They are responsible for control and intermediate storage of the data to and from the cabinet.
Detailed description of exemplary embodiments:
A known IMA- (integrated modular avionics) architecture according to Fig. 1 provides several cabinets at various locations in the aircraft. Each cabinet comprises the follow-ing modules: power supply modules (PSM), I/O modules (IOM), and core processing modules (CPM). All modules receive electrical power from the power supply and are interconnected for data exchange by way of a backplane bus (Arinc 659 - a SAFEbus by Honeywell).
The sensor data of the various functions are transmitted to the core processor by way of the input modules and the backplane bus. In the core processor an operating system de-termines which system software (application) is to be used at what time. The data is directly transmitted to the associated software. After completion of processing, the data are returned via the backplane bus to the output module from where they are transmitted to actuators or other systems. The cabinets in turn are interconnected in a network (Arinc 629).
In this solution the backplane bus represents a bottleneck. In order to prevent a collapse, the data haveto be determined deterministically for transmission.
In order to obviate the need for such a backplane bus and in this way to avoid the asso-ciated bottleneck, an architecture for a cabinet is proposed, which architecture is based on parallel processors, for example transputers. The IMA architecture according to Fig.
2 shows this configuration.
For reasons of redundancy the cabinet comprises at least two core processor modules (CPM1, CPM2) and at least two input/output modules (IOM1, IOM2).
The IOMs are used as an interface to the sensors, actuators, systems and buses. They are responsible for control and intermediate storage of the data to and from the cabinet.
5 Each core processor independently communicates, by way of links, with each IOM
module and CPM module. In the CPM a number of independent system programs work under the control of an operating system.
This architecture, which is based on transputers, provides the following advantages when compared to prior art:
1. No central data bus and no bidirectional databuses but only unidirectional databuses are used so that no data conflicts in the buses can occur.
2. No tools for the design of deterministic data traffic are required.
3. Changes in the applications are possible without making a change of a bus data-structure necessary.
module and CPM module. In the CPM a number of independent system programs work under the control of an operating system.
This architecture, which is based on transputers, provides the following advantages when compared to prior art:
1. No central data bus and no bidirectional databuses but only unidirectional databuses are used so that no data conflicts in the buses can occur.
2. No tools for the design of deterministic data traffic are required.
3. Changes in the applications are possible without making a change of a bus data-structure necessary.
Claims (2)
1. A modular avionics system of an aircraft, comprising several cabinets that are arranged at various locations in the aircraft and that are interconnected in a network, which cabinets are used for controlling or processing signals that are transmitted from sensors and/or from and to actuators and other systems of the aircraft, wherein - the system comprises parallel processors;
- the cabinets comprise at least two core processor modules (CPM1, CPM2) and at least two input/output modules (IOM1, IOM2);
- the input/output modules (IOM1, IOM2) serve as interfaces to the sys-tems to be controlled, and serve for the control and intermediate stor-age of the data flowing into or out of the cabinet;
characterised in that - each core processor module (CPM1, CPM2) communicates independ-ently, by way of unidirectional separate direct data lines, with each IOM module and CPM module; and - in each core processor a number of independent system programs work under the control of an operating system.
- the cabinets comprise at least two core processor modules (CPM1, CPM2) and at least two input/output modules (IOM1, IOM2);
- the input/output modules (IOM1, IOM2) serve as interfaces to the sys-tems to be controlled, and serve for the control and intermediate stor-age of the data flowing into or out of the cabinet;
characterised in that - each core processor module (CPM1, CPM2) communicates independ-ently, by way of unidirectional separate direct data lines, with each IOM module and CPM module; and - in each core processor a number of independent system programs work under the control of an operating system.
2. The modular avionics system according to claim 1, characterised in that the configuration of the system is realized with transputers that are considered in-stead of parallel processors.
Applications Claiming Priority (3)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| DE102005055000A DE102005055000A1 (en) | 2005-11-18 | 2005-11-18 | Modular avionics system of an aircraft |
| DE102005055000.2 | 2005-11-18 | ||
| PCT/EP2006/011010 WO2007057189A1 (en) | 2005-11-18 | 2006-11-16 | Modular avionics system of an aircraft |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CA2627492A1 true CA2627492A1 (en) | 2007-05-24 |
Family
ID=37836801
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CA002627492A Abandoned CA2627492A1 (en) | 2005-11-18 | 2006-11-16 | Modular avionics system of an aircraft |
Country Status (9)
| Country | Link |
|---|---|
| US (1) | US8255095B2 (en) |
| EP (1) | EP1949248A1 (en) |
| JP (1) | JP2009516275A (en) |
| CN (1) | CN101310266A (en) |
| BR (1) | BRPI0617882A2 (en) |
| CA (1) | CA2627492A1 (en) |
| DE (1) | DE102005055000A1 (en) |
| RU (1) | RU2413655C2 (en) |
| WO (1) | WO2007057189A1 (en) |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN105373136A (en) * | 2014-10-22 | 2016-03-02 | 航天恒星科技有限公司 | Integrated electronic system based on VPX architecture |
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| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| FR2920410B1 (en) * | 2007-09-03 | 2009-10-30 | Airbus France Sas | DISTRIBUTED ARCHITECTURE BETWEEN A FADEC AND AVIONIC COMPONENTS |
| DE102007052139A1 (en) * | 2007-10-31 | 2009-05-20 | Airbus Deutschland Gmbh | Method for providing fault diagnose for system, particularly airplane, involves providing number of systems, where one of system provides number of instances of main function of number of main functions of airplane |
| US8467913B2 (en) | 2007-10-31 | 2013-06-18 | Airbus Operations Gmbh | Method and arrangement for providing a fault diagnosis for at least one system |
| FR2926375B1 (en) * | 2008-01-11 | 2010-02-12 | Airbus France | METHOD FOR PERFORMING COMPUTER APPLICATION, KIT AND AIRCRAFT |
| US8370002B2 (en) * | 2009-04-03 | 2013-02-05 | The Boeing Company | Multi-mission remote aerial refueling operator system |
| US8295995B2 (en) * | 2009-04-22 | 2012-10-23 | Hamilton Sundstrand Corporation | Distributed approach to electronic engine control for gas turbine engines |
| FR2945647A1 (en) * | 2009-05-18 | 2010-11-19 | Airbus France | METHOD OF OPTIMIZING AN AVIONIC PLATFORM |
| FR2945646B1 (en) | 2009-05-18 | 2012-03-09 | Airbus France | METHOD FOR AIDING THE REALIZATION AND VALIDATION OF AN AVIONIC PLATFORM |
| DE102009041599A1 (en) | 2009-09-15 | 2011-04-14 | Airbus Operations Gmbh | A control device, input / output device, connection switching device and method for an aircraft control system |
| JP5607919B2 (en) * | 2009-12-16 | 2014-10-15 | 川崎重工業株式会社 | Integrated airborne electronic system |
| FR2960668A1 (en) * | 2010-05-27 | 2011-12-02 | Airbus Operations Sas | METHOD AND DEVICE FOR INCREMENTAL CONFIGURATION OF IMA TYPE MODULES |
| FR2960680B1 (en) * | 2010-05-28 | 2013-05-17 | Airbus Operations Sas | ON-BOARD AIRCRAFT SYSTEM |
| US20110308823A1 (en) * | 2010-06-17 | 2011-12-22 | Dharmendr Len Seebaluck | Programmable controller for a fire prevention system |
| US20120095663A1 (en) * | 2010-10-14 | 2012-04-19 | Hamilton Sundstrand Corporation | Fmu mounted eec for small aircraft engine applications |
| US20120203401A1 (en) * | 2011-02-08 | 2012-08-09 | Jonathan Mark Dunsdon | Onboard Maintenance System Network Optimization |
| RU2595507C2 (en) * | 2014-04-21 | 2016-08-27 | Открытое Акционерное Общество "Авиационная Холдинговая Компания "Сухой" | Platform of integrated modular avionics combat systems |
| CN104866355B (en) * | 2015-05-29 | 2018-04-17 | 中国航空无线电电子研究所 | One kind is applied to IMA systematic difference Design for polymorphism methods |
| CN105549462A (en) * | 2015-12-09 | 2016-05-04 | 中国航空工业集团公司西安航空计算技术研究所 | Avionic task integrated processing system |
| CN105553592B (en) * | 2015-12-10 | 2018-04-17 | 中国航空工业集团公司西安航空计算技术研究所 | A kind of IMA processor systems clock synchronizing method |
| FR3045852B1 (en) * | 2015-12-16 | 2018-02-02 | Thales | METHOD FOR TRANSMITTING MESSAGES WITH TEMPORAL SETTING BETWEEN ELECTRONIC MODULES, AVIONIC SYSTEM AND CONFIGURATION METHOD |
| CN106681957A (en) * | 2016-12-26 | 2017-05-17 | 中国航空工业集团公司西安飞机设计研究所 | Distributed modularization avionic core processing platform architecture |
| FR3071980B1 (en) * | 2017-10-04 | 2019-09-27 | Airbus Operations | DEVICE FOR EXTENDING PORTS FOR AN AIRCRAFT |
| RU189187U1 (en) * | 2018-06-20 | 2019-05-15 | Акционерное общество "Саратовский электроприборостроительный завод имени Серго Орджоникидзе" | ONBOARD COMPUTING SYSTEM FOR INTEGRATED MODULAR AVIONICS |
| US11048389B2 (en) * | 2019-09-16 | 2021-06-29 | Mid-Continent Instrument Co., Inc. | Customizable multi-function display |
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| US4658359A (en) * | 1984-12-31 | 1987-04-14 | The United States Of America As Represented By The Secretary Of The Navy | Method for managing redundant resources in a complex avionics communication system |
| US5361367A (en) * | 1991-06-10 | 1994-11-01 | The United States Of America As Represented By The Administrator Of The National Aeronautics And Space Administration | Highly parallel reconfigurable computer architecture for robotic computation having plural processor cells each having right and left ensembles of plural processors |
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| RU12478U1 (en) | 1999-09-07 | 2000-01-10 | Общество с ограниченной ответственностью "Авионика-Вист" | MULTIFUNCTIONAL ON-BOARD COMPUTER COMPLEX |
| RU2163728C1 (en) | 2000-02-29 | 2001-02-27 | Общество с ограниченной ответственностью "Авионика-Вист" | Data exchange multiplex channel adapter |
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| FR2819598B1 (en) * | 2001-01-16 | 2003-04-11 | Thomson Csf | FAULT-TOLERANT SYNCHRONIZATION DEVICE FOR A REAL-TIME COMPUTER NETWORK |
| US6654685B2 (en) * | 2002-01-04 | 2003-11-25 | The Boeing Company | Apparatus and method for navigation of an aircraft |
| US20050216700A1 (en) * | 2004-03-26 | 2005-09-29 | Hooman Honary | Reconfigurable parallelism architecture |
| US7421526B2 (en) * | 2005-08-24 | 2008-09-02 | Honeywell International Inc. | Reconfigurable virtual backplane architecture |
| US8467913B2 (en) * | 2007-10-31 | 2013-06-18 | Airbus Operations Gmbh | Method and arrangement for providing a fault diagnosis for at least one system |
-
2005
- 2005-11-18 DE DE102005055000A patent/DE102005055000A1/en not_active Ceased
-
2006
- 2006-11-16 US US12/085,012 patent/US8255095B2/en active Active
- 2006-11-16 CN CNA2006800426525A patent/CN101310266A/en active Pending
- 2006-11-16 WO PCT/EP2006/011010 patent/WO2007057189A1/en active Application Filing
- 2006-11-16 RU RU2008123940/11A patent/RU2413655C2/en not_active IP Right Cessation
- 2006-11-16 EP EP06818597A patent/EP1949248A1/en not_active Ceased
- 2006-11-16 CA CA002627492A patent/CA2627492A1/en not_active Abandoned
- 2006-11-16 BR BRPI0617882-0A patent/BRPI0617882A2/en not_active IP Right Cessation
- 2006-11-16 JP JP2008540518A patent/JP2009516275A/en active Pending
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN105373136A (en) * | 2014-10-22 | 2016-03-02 | 航天恒星科技有限公司 | Integrated electronic system based on VPX architecture |
Also Published As
| Publication number | Publication date |
|---|---|
| RU2413655C2 (en) | 2011-03-10 |
| DE102005055000A1 (en) | 2007-05-24 |
| US8255095B2 (en) | 2012-08-28 |
| BRPI0617882A2 (en) | 2011-08-09 |
| JP2009516275A (en) | 2009-04-16 |
| EP1949248A1 (en) | 2008-07-30 |
| RU2008123940A (en) | 2009-12-27 |
| US20100153684A1 (en) | 2010-06-17 |
| CN101310266A (en) | 2008-11-19 |
| WO2007057189A1 (en) | 2007-05-24 |
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